Device for removing debris from an aerodynamic structure

Abstract

A device for removing debris, such as insects and ice, from an aerodynamic structure of an aircraft and in which the aerodynamic structure has upper and lower surfaces separated by a leading edge extending along the length of the aerodynamic structure. The device includes a spine positionable so as to extend between the upper and lower surfaces over the leading edge of the aerodynamic structure, a scraping edge carried by the spine facing a direction that extends along the length, and a drive mechanism configured to move the spine in the direction so that the scraping edge scrapes debris from along the length of the aerodynamic structure. The spine is configured to bias the scraping edge against the aerodynamic structure.

The invention is: 
     
         1 . A device for removing debris from an aerodynamic structure of an aircraft, wherein the aerodynamic structure includes upper and lower surfaces separated by a leading edge extending along a length of the aerodynamic structure, the device comprising:
 a spine positionable so as to extend between the upper and lower surfaces over the leading edge of the aerodynamic structure,   a scraping edge carried by the spine facing a direction that extends along the length, and   a drive mechanism configured to move the spine in the direction so that the scraping edge scrapes debris from along the length of the aerodynamic structure,   wherein the spine is flexible and includes an elongate main body and a flange extending from a longitudinal edge of the main body, the scraping edge being formed at an end of the flange remote from the main body, the device further comprising a biasing element mounted to the main body to bias the scraping edge against the aerodynamic structure.   
     
     
         2 . The device according to  claim 1 , wherein the spine is configured to bias the scraping edge against the aerodynamic structure along the length of the spine. 
     
     
         3 . The device according to  claim 1 , wherein the main body comprises a base wall positionable against the aerodynamic structure and another wall extending upwardly from the base in a direction away from the aerodynamic structure to define a recess along the spine, the biasing element being received in the recess. 
     
     
         4 . The device according to  claim 3 , wherein the flange extends from the another wall and the biasing element is configured to act on the another wall to deflect the flange and bias the scraping edge against the aerodynamic surface. 
     
     
         5 . The device according to  claim 4 , wherein the another wall is divided into sections by slots in the main body. 
     
     
         6 . The device according to  claim 3 , wherein a heating element is received in the flange adjacent to the scraping edge and extends along the spine. 
     
     
         7 . The device according to  claim 6 , wherein the flange comprises a plurality of spaced connecting arms extending between the another wall and the scraping element. 
     
     
         8 . The device according to  claim 7 , wherein the heating element is received in a space in the flange beneath the spaced connecting arms. 
     
     
         9 . The device according to  claim 3 , wherein a flange extends from each of opposing longitudinal edges of the main body and the scraping edge includes scraping elements, each flange including one or more of the scraping elements that faces such that the scraping element on the flange on one of the edges of the main body extends in an opposite direction to the scraping element on the flange extending from the opposite edge of the main body, wherein the biasing element is configured to bias each scraping element against the aerodynamic surface. 
     
     
         10 . The device according to  claim 3 , wherein the biasing element comprises a plurality of springs spaced from each other along the length of the spine and positioned so as to apply a biasing force to the flange to urge the scraping edge in a direction towards the aerodynamic surface. 
     
     
         11 . The device according to  claim 1 , wherein the drive mechanism is positionable within the aerodynamic structure for connection to the spine extending between the upper and lower surfaces and over the leading edge of the aerodynamic structure. 
     
     
         12 . The device according to  claim 1 , wherein the spine is formed from heat resistant polycarbonate. 
     
     
         13 . An aerodynamic structure incorporating the device for removing debris according to  claim 1 . 
     
     
         14 . A device configured to be mounted to an aerodynamic structure a leading edge extending a length of a span of the structure and upper and lower surfaces extending reward of the leading edge in a chord direction, the device comprising:
 a flexible spine including an elongate main body and a flange extending from a longitudinal edge of the main body, wherein the elongate main body is oriented parallel to a chord of the aerodynamic structure and the main body is configured to seat on and abut the leading edge;   a scraping edge on a longitudinal edge of the flange opposite to an edge of the flange attached to the main body;   a drive mechanism coupled to the flexible spine and to the aerodynamic structure, wherein the drive mechanism is configured to slide the spine along the span of the aerodynamic structure; and   a biasing element mounted to the main body and configured to bias the scraping edge against the aerodynamic structure.   
     
     
         15 . The device of  claim 14  further comprising a second flange extending from a second longitudinal edge of the main body, and a second scraping edge on a longitudinal edge of the second flange which is opposite to an edge of the second flange adjacent the main body. 
     
     
         16 . The device of  claim 14  wherein the biasing element is a plurality of biasing elements mounted to the main body of the flexible spine and each applying a biasing force to the flange. 
     
     
         17 . A method to remove debris from an aerodynamic structure of an aircraft, the method comprising:
 while the aircraft is moving, sliding a flexible spine across a leading edge of the aerodynamic structure, wherein the flexible spine has a length in a direction of a chord of the aerodynamic structure greater than a width in a direction of a span of the aerodynamic structure;   as the flexible spine slides across the leading edge, removing debris on the leading edge with a scraping edge on at least one side of the flexible spine, and   biasing the scraping edge against the leading edge and at least one of an upper or lower surface of the aerodynamic surface while the flexible spine slides across the leading edge.   
     
     
         18 . The method of  claim 17  wherein the biasing includes biasing an entire length of the scraping edge against the leading edge and the at least one of an upper or lower surface of the aerodynamic surface. 
     
     
         19 . The method of  claim 17  wherein the flexible spine includes an elongate main body oriented in the direction of the chord and an elongate flange extending from a side of the main body, wherein the scraping edge is on an edge of the elongate flange opposite to an edge of the flange adjacent the main body, and the biasing of the scraping edge includes biasing the flange by a biasing element mounted to the main body.